Designed by Robert Barrows of Fincastle, Virginia, the Bearhawk is a 4-place built design with generous proportions and superior performance. The design parameter were for a heavy hauling BIG airplane with a good cruise speed and economical operation. Short field performance is excellent with the large flaps. The Bearhawk is a 4 place and the prototype Bearhawk N6890R is powered by a Lycoming O-360 (170 hp) set up to burn auto fuel.
The Bearhawk has an all metal wing with a fabric covered steel tube fuselage and tail feathers. A Cessna windshield, modified lift struts, and the fiberglass nose bowl are some airframe components that need not be built by the homebuilder. The builder time is estimated at 1500-2000 hrs.
Courtesy Mark Winfield Scott
Engine: Lycoming O-360, 170 hp HP range: 150-260 Wing Span: 33 ft. Wing Area: 180 ft. Length: 23 ft. 6 in. Height: 7 ft Empty Weight: 1190 lbs. Gross Weight: 2500 lbs. Fuel cap: 55 USG Top Speed (VNE): 175 mph Cruise Speed: 120-150 mph Landing Speed: 40 mph Take Off Roll: 250-600 ft. Range (55 gal @ 60%): 800 miles Stall: 40 mph ROC: 1500 fpm Range: 800 sm Service ceiling: 15,000 ft Cabin Width: 42 in. Cabin Length (Firewall to the end of baggage area): 9 ft. 8 in Cockpit width: 30 in Landing gear: tail wheel Seats: 4
Raytheon Aircraft won a USAF and USN Joint Primary Aircraft Training System competition with the Beech Mk.II trainer, derived from the Pilatus PC-9.
Raytheon’s contract with the U.S. joint armed services to provide up to 700 T-6ATexan II JPATS trainers through the year 2014 continued to pay dividends for the Wichita based airframer. The Air Force and Navy exercised an option for 22 additional Texan IIs, an order valued at almost $65 million.
The first production T-6A Texan II flew on 15 July 1998.
Apart from the JPATS program, Raytheon has orders for 138 T 6As, including a 45 airplane deal with the Greek Air Force.
The first production Beechcraft AT-6 light attack aircraft made a ceremonial first flight on 20 August 2013 at Wichita, Kansas. The single-engined 1,600shp (1,190kW) Pratt & Whitney PT6 turboprop aeroplane took to the air at about 10:30 local time with test pilot Lionel Alford at the controls.
The aircraft was loaded with a pair of 66 gal (250 litres) drop tanks, two inert GBU-58 laser-guided bombs and two LAU-131 seven-shot rocket launchers. The AT-6 was also carrying a L-3 Wescam Mx-15Di electro-optical infrared camera. Although a production aircraft, it is a company-owned asset. Beechcraft has not secured an order for the type. When asked why the company would fly the first flight with such a heavy load, Derek Hess, the company’s senior vice-president for business development, says: “Because it’s so easy.”
The aircraft had demonstrated air-to-air gunnery with .50 caliber machine guns and the potential exists to employ Raytheon AIM-9 Sidewinders to counter certain aerial threats.
T-6C Texan II
The AT-6TH Wolverine attack variant is derived from the T-6C Texan trainer and is designed to carry out close air support and surveillance missions. The AT-6 has an L3 Wescam MX-15D multi-sensor package that includes colour and IR cameras, laser designator, laser illuminator, and laser rangefinder.
Royal Thai Air Force AT-6TH Wolverine
The Royal Thai Air Force (RTAF) received eight AT-6TH Wolverine light attack aircraft in 2025 acquired from the United States as part of its ongoing fleet modernization program.
Assigned to Squadron 411, part of Wing 41 based in Chiang Mai, the AT-6TH Wolverine, manufactured by U.S. company Textron Aviation, is designed for close air support, armed surveillance, and tactical training missions.
T-6A Texan II Engine: Pratt & Whitney Canada PT6A-68, 1100 hp Length: 33.268 ft / 10.14 m Height: 10.696 ft / 3.26 m Wingspan: 33.301 ft / 10.15 m Wing area: 175.346 sq.ft / 16.29 sq.m Max take off weight: 6299.7 lb / 2857.0 kg Weight empty: 4601.8 lb / 2087.0 kg Max. speed: 310 kt / 575 km/h Cruising speed: 230 kt / 426 km/h Initial climb rate: 3996.06 ft/min / 20.30 m/s Service ceiling: 35007 ft / 10670 m Wing loading: 35.88 lb/sq.ft / 175.0 kg/sq.m Range: 850 nm / 1574 km Endurance: 3 h Crew: 2
Rawdon Brothers, a flying school operator, designed and built a Lycoming engined two-seat monoplane, the T-1, first produced in 1938. At least five were produced pe-war.
The design was resurrected in 1953, powered by a 135 hp Lycoming engine.
The T-1S is an agricultural version equipped with spray tanks and spray bars.
Engine: Lycoming O-290 Max speed: 138 mph Cruise: 120 mph ROC: 900 fpm Service ceiling: 18,000 ft Range: 500 mi Empty weight: 1300 lb Loaded weight: 1900 lb Wingspan: 33 ft 4 in Length: 24 ft 2 in Height: 7 ft 3 in
First flown in 1996, development/testing continued into 2008. With ongoing changes in the Ultralight/Light Sport arena, development of both the FAR Part 103 legal Ultralight gyro and the 2-3 seat cargo twin-engine gyro were put on hold.
Taildragger landing gear with large “tundra tires”, cable braced tempered aluminum main gear, and steerable tailwheel for superior handling off runway on rough terrain.
Conventional elevator control in the pitch axis are to minimize “porpoising” and “bunt-over”. A chrome-moly roll cage construction with pilot enclosure and lexan windshield are provided.
An optional pre-rotator assembly is available for reduced take off distance.
Introduced in 2009, the Raven 2XS (English: To Excess) is a Canadian aerobatic amateur-built biplane, designed and produced by Raven Aircraft of Surrey, British Columbia. The aircraft is supplied as a kit or as plans for amateur construction.
Developed from the Pitts Special, the 2XS features a strut-braced biplane layout, a two-seats-in-tandem enclosed cockpit under a bubble canopy, fixed conventional landing gear and a single engine in tractor configuration. The cockpit is 24 in (61 cm) wide.
The aircraft is made from mixed construction, using welded steel tubing, aluminum and wood, with its flying surfaces covered in doped aircraft fabric. Construction time from the supplied kit is estimated as 2000 hours.
By November 2012 one example had been registered in the United States with the Federal Aviation Administration, but none in its home country with Transport Canada. Unit cost: US$24,000 (kit only, less engine, instruments, 2011)
Engine: 1 × Lycoming IO-540, 280 hp (210 kW) HP range: 260-400 Propellers: 3-bladed composite Length: 19 ft 4 in (5.89 m) Wingspan: 19 ft 2 in (5.84 m) Height: 6 ft 6 in (1.98 m) Wing area: 119.4 sq ft (11.09 m2) Empty weight: 1,180 lb (535 kg) Gross weight: 1,780 lb (807 kg) Fuel capacity: 37 U.S. gallons (140 L; 31 imp gal) Maximum speed: 200 mph (322 km/h; 174 kn) Cruise speed: 188 mph (163 kn; 303 km/h) Stall speed: 60 mph (52 kn; 97 km/h) Range: 450 mi (391 nmi; 724 km) Rate of climb: 3,300 ft/min (17 m/s) Wing loading: 14.9 lb/sq ft (73 kg/m2) Roll rate: 330 degrees/second. Takeoff dist: 530 ft Landing dist: 750 ft Seats: 2 tandem Cockpit width: 24 in Landing gear: tailwheel
This composite aircraft, based on the concept of the Piper Comanche was designed and developed by SA Ravin in 2 years and 5 months. The Ravin 500 made it’s first flight on 15 September 2002.
An all Composite kit aircraft for amateur construction by SA Ravin Aircraft of Pretoria, South Africa.
An NACA 64-series profile (modified) was used, brought into the shape by Francois Jordaan. The standard handshake overlap main spar design is used to join the two spars in the fuselage.
A Hartzell 3 Bladed Scimitar Pulse Prop was used from the beginning. It uses a 12 liter plenim box in conjunction with the air filter.
The fuselage mold is split vertically with port and starboard halves. There are cross braces below the cockpit floor and one bulkhead visible in the rear fuselage.
Wings are also two-piece, incorporating mainspars and rear subspars. The carbon mainspars overlap and join within the fuselage. Horizontal tailplane was one-piece, glass with carbon elevator.
The fuselage, wings, tailplane and other components appear to have been molded with an inscribed grid covering the exterior surfaces as an aid to alignment and windshield, window cutouts.
Ravin 500 Type: 4-Seat cruiser, conventional Engine: Lycoming IO540 (194kW, 260h) Wing span: 10,40m (34ft 2 in) Wing Area: 14,6 sq m (157 sq ft) Empty Weight: 975 kg – 1040 kg Max take-off Weight: 1620 kg (3564 lb) Aircraft Length: 7,42 m (24 ft 4 ins) Fuel Capacity: 160 US gal integral wing tanks Max power loading: 8.35 kg/sq m (22.7 lb/hp) Max wing loading: 111 kg/sq m (22.7 lb/sq ft) Max level speed (sea level ISA): 210 kts (242 mph) IAS Cruise speed (75% power): 185 kts (213 mph) IAS Optimum cruise (75%@ 6500 ft): 196 kts (226 mph) TAS Stall speed clean @ max weight: 64 kts IAS (75 mph) IAS Stall speed with flaps, gear down: 56 kts IAS (64 mph) IAS Fuel consumption @ 75% power: 14.1 US gal/hr Range with 10% fuel reserve: 2000 naut miles (2300 stat miles)
The Aeroscaphe of Ravard was a machine designed to move either on water or in air. It was an aeroplane with pontoons or floaters. The supporting surface aggregated 400 square feet, and the gross weight was about 1100 pounds. A fifty horse-power Gnome seven-cylinder motor at 1200 revolutions drove two propellers of eight and ten and one-half feet diameter respectively: the propellers being mounted one behind the other on the same shaft.
In 1933 Hans L Rasmussen built the Rasmussen Skippy racer N13518 for the 1934 Nationals, and its radial engine (with four valves each), were both built by machinist Rasmussen.
Racing was piloted by Bill Kysor.
After the races a top wing was added as a sport plane conversion.
All Aero 